LecturePg. 55-60.The creep properties of gas turbine blades will deteriorate with prolonged service exposure. This deterioration is primarily due to internal microstructural changes and the formation of creep voids or cavitation. Development work has shown that HIP processing is the best available treatment for recovery of properties in used blades. The results obtained on a complete engine set of lnconel X-750 blades indicate that HIP processing is capable of restoring new or near new creep resistance to used blades
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...
AbstractMany hot gas components in gas turbine are made of Ni-based superalloy because of their high...
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...
LecturePg. 21-30The first task in extending the life of gas turbine parts is to develop meaningful l...
A HIP rejuvenation study for an aluminide coated, internally cooled IN 738, turbine blade from an ae...
The turbine blades in aircraft engines are subjected to a complex combination of stresses. With hot-...
LecturePg. 113-124The practice of rejuvenating reheat treatments, with and without hot isostatic pre...
This paper deals with assessment of high temperature force controlled fatigue and creep properties o...
Impact of heat treatment on hot isostatically pressed (HIP) Ni-base superalloy has been investigated...
High Pressure Turbine (HPT) first stage blade is the most important rotational components of aero-e...
One of the important units in a gas turbine is the turbine blades. Turbine blades are exposed to the...
High Pressure Turbine (HPT) first stage blade is the most important rotational components of aero-e...
The Udimet 500 nickel base superalloy blade exposed for 50000 hours in land base gas turbine working...
Impact of heat treatment on hot isostatically pressed (HIP) Ni-base superalloy has been investigated...
Turbine blades are flight safety parts in the jet engine. Therefore they should be characterized by ...
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...
AbstractMany hot gas components in gas turbine are made of Ni-based superalloy because of their high...
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...
LecturePg. 21-30The first task in extending the life of gas turbine parts is to develop meaningful l...
A HIP rejuvenation study for an aluminide coated, internally cooled IN 738, turbine blade from an ae...
The turbine blades in aircraft engines are subjected to a complex combination of stresses. With hot-...
LecturePg. 113-124The practice of rejuvenating reheat treatments, with and without hot isostatic pre...
This paper deals with assessment of high temperature force controlled fatigue and creep properties o...
Impact of heat treatment on hot isostatically pressed (HIP) Ni-base superalloy has been investigated...
High Pressure Turbine (HPT) first stage blade is the most important rotational components of aero-e...
One of the important units in a gas turbine is the turbine blades. Turbine blades are exposed to the...
High Pressure Turbine (HPT) first stage blade is the most important rotational components of aero-e...
The Udimet 500 nickel base superalloy blade exposed for 50000 hours in land base gas turbine working...
Impact of heat treatment on hot isostatically pressed (HIP) Ni-base superalloy has been investigated...
Turbine blades are flight safety parts in the jet engine. Therefore they should be characterized by ...
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...
AbstractMany hot gas components in gas turbine are made of Ni-based superalloy because of their high...
Tutorialpg. 197-214Material issues are of paramount importance for the reliable and cost effective ...